Optimal Control of Orbit Transfer of Space Probe with Limit Thrust
- Paper number
IAC-05-A3.P.09
- Author
Dr. Xingsuo He, Northwestern Polytechnical University, China
- Coauthor
Mrs. Ping Wang, Northwestern Polytechnical University, China
- Year
2005
- Abstract
The minimum-fuel orbit transfer of space probe with limit thrust is studied in view of the principle of saving energy in this paper. The optimization of the dynamic equations including the control parameters shows that the optimal values are constants. According to general cases of orbit transfer,the authors select the initial true anomaly,yaw angle and the dive angle as the starting values of the iteration method, and accomplish the optimization task to the equations which contain control variables using the maximum value principle. In the cases both yaw angle and the dive angle are constant value and based on the "target method" of the nonlinear Two-point Boundary Value Problems for solving differential equations, the paper studies the selection of free initial values and the terminal constraint of the Two-point Boundary Value Problems. Finally two numerical example of optimal orbit transfer of Mars probe are calculated and discussed. The results show the optimal method is feasible. The method in this paper provides designing basis and theoretical reserve for the space exploration engineering, and is of very important theoretical significance and reference value for the development, advance and progress of the international aerospace science and technology.
- Abstract document
- Manuscript document
IAC-05-A3.P.09.pdf (🔒 authorized access only).
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